DOC AIRBUS | MMEL OPS PROCGround Spoiler Control System (Ground spoiler control system inoperative)
| 27-92-02A | Ground Spoiler Control System (Ground spoiler control system inoperative) |
|---|
Applicable to: -
- General information
The autobrake function is
not available. Refer to OpsProc AUTO/BRK Function
| CAUTION: | One or both thrust
reversers may not deploy at landing. Consequently, for performance
determination, do not take into account the credit of the thrust reversers. |
- Flight preparation/limitations
The following penalties
may be used for takeoff and landing performance determination if no
takeoff and landing data (predetermined by using OCTOPUS program or
other equivalent program with present failure case) is available.
Takeoff performance computation:
The method explained hereafter
allows the determination of the MTOW and associated speeds
(V1, VR, V2), by applying decrements
on the MTOW and associated speeds computed in normal conditions
(i.e. all systems operative).
| WARNING: |
|
How to proceed ?
- Read, in 0 kt wind column of the takeoff chart computed in normal condition, the MTOW and associated speeds (V1, VR, V2) corresponding to the actual temperature, even in the case of headwind (the method does not take into account the headwind benefit on takeoff performance).
- Apply the QNH and/or bleed corrections, if any, to determine the MTOW.
- Enter the following table to determine the MTOW and speed decrements.
- Applying these decrements, calculate the MTOW and associated speeds corresponding to the actual temperature.
| CAUTION: | For runway lengths below 1,500
m, do not use the following table. |
DECREMENTS (ΔW, ΔV1, ΔVR, ΔV2) WHEN GROUND SPOILER CONTROL
SYSTEM IS INOPERATIVE | ||||||||||||
|---|---|---|---|---|---|---|---|---|---|---|---|---|
| RUNWAY LENGTH (m) | CONFIGURATION | |||||||||||
| 1+F | 2 | 3 | ||||||||||
| ΔW (kg/lb) | ΔV1 (kt) | ΔVR (kt) | ΔV2 (kt) | ΔW (kg/lb) | ΔV1 (kt) | ΔVR (kt) | ΔV2 (kt) | ΔW (kg/lb) | ΔV1 (kt) | ΔVR (kt) | ΔV2 (kt) | |
| 1500 | 1000 / 2200 | 3 | 1 | 1 | 1000 / 2200 | 3 | 1 | 1 | 1500 / 3300 | 4 | 1 | 1 |
| 2000 | 1000 / 2200 | 4 | 1 | 1 | 1300 / 2900 | 4 | 1 | 1 | 1000 / 2200 | 5 | 2 | 2 |
| 2500 | 1000 / 2200 | 4 | 1 | 1 | 1300 / 2900 | 5 | 2 | 2 | 1000 / 2200 | 8 | 3 | 3 |
| 3000 | 1000 / 2200 | 5 | 2 | 2 | 1300 / 2900 | 6 | 3 | 3 | 1000 / 2200 | 10 | 4 | 4 |
| 3500 | 2000 / 4400 | 8 | 3 | 3 | 2000 / 4400 | 8 | 4 | 4 | 1300 / 2900 | 11 | 5 | 5 |
| 4000 and above | 2000 / 4400 | 9 | 3 | 3 | 2000 / 4400 | 9 | 5 | 5 | 1500 / 3300 | 9 | 4 | 4 |
If the actual TOW is lower than the MTOW calculated using above method:
The speeds determined
without failure and associated with the actual TOW may
be retained provided that they are all lower than the speeds calculated
using above method.
Check that the corrected V1 is equal to or above the minimum V1 value shown
on the RTOW chart (due to VMCG limitation).
If the corrected V1 is lower than the minimum V1:
Take this last value
as V1.
Further decrease the weight by 3000 kg ( 6600 lb) per kt difference between both values.
Check that the corrected VR is equal to or above the minimum VR value shown
on the RTOW chart (due to VMCA limitation).
If the corrected VR is lower than the minimum VR:
Takeoff cannot be performed using this method.
Check that the corrected V2 is equal to or above the minimum V2 value shown
on the RTOW chart (due to VMCA limitation).
If the corrected V2 is lower than the minimum V2:
Takeoff cannot be performed using this method.
Check that the corrected V2 is equal to or above the minimum V2 due to VMU limitation ( Refer to FCOM).
If the corrected V2 is lower than the minimum V2:
Takeoff cannot be performed using this method.
Landing performance computation:
Multiply the landing distances by 1.20.
- Takeoff
If the above method was used for takeoff performance computation:
Perform the takeoff
using full thrust (TOGA).
| 27-92-02A | Ground Spoiler Control System (Ground spoiler control system inoperative) |
|---|
Applicable to: -
- General information
The autobrake function is
not available. Refer to OpsProc AUTO/BRK Function
| CAUTION: | One or both thrust
reversers may not deploy at landing. Consequently, for performance
determination, do not take into account the credit of the thrust reversers. |
- Flight preparation/limitations
The following penalties
may be used for takeoff and landing performance determination if no
takeoff and landing data (predetermined by using OCTOPUS program or
other equivalent program with present failure case) is available.
Takeoff performance computation:
The method explained hereafter
allows the determination of the MTOW and associated speeds
(V1, VR, V2), by applying decrements
on the MTOW and associated speeds computed in normal conditions
(i.e. all systems operative).
| WARNING: |
|
How to proceed ?
- Read, in 0 kt wind column of the takeoff chart computed in normal condition, the MTOW and associated speeds (V1, VR, V2) corresponding to the actual temperature, even in the case of headwind (the method does not take into account the headwind benefit on takeoff performance).
- Apply the QNH and/or bleed corrections, if any, to determine the MTOW.
- Enter the following table to determine the MTOW and speed decrements.
- Applying these decrements, calculate the MTOW and associated speeds corresponding to the actual temperature.
| CAUTION: | For runway lengths below 1,500
m, do not use the following table. |
DECREMENTS (ΔW, ΔV1, ΔVR, ΔV2) WHEN GROUND SPOILER CONTROL
SYSTEM IS INOPERATIVE | ||||||||||||
|---|---|---|---|---|---|---|---|---|---|---|---|---|
| RUNWAY LENGTH (m) | CONFIGURATION | |||||||||||
| 1+F | 2 | 3 | ||||||||||
| ΔW (kg/lb) | ΔV1 (kt) | ΔVR (kt) | ΔV2 (kt) | ΔW (kg/lb) | ΔV1 (kt) | ΔVR (kt) | ΔV2 (kt) | ΔW (kg/lb) | ΔV1 (kt) | ΔVR (kt) | ΔV2 (kt) | |
| 1500 | 2400 / 5300 | 6 | 2 | 2 | 2200 / 4900 | 7 | 5 | 5 | 3000 / 6700 | 8 | 7 | 7 |
| 2000 | 1400 / 3100 | 6 | 3 | 3 | 1600 / 3600 | 7 | 4 | 4 | 1800 / 4000 | 8 | 4 | 4 |
| 2500 | 1400 / 3100 | 5 | 3 | 3 | 1400 / 3100 | 7 | 4 | 4 | 1800 / 4000 | 9 | 5 | 5 |
| 3000 | 1400 / 3100 | 8 | 5 | 5 | 1200 / 2700 | 8 | 5 | 5 | 1200 / 2700 | 9 | 6 | 6 |
| 3500 | 1400 / 3100 | 8 | 5 | 5 | 1000 / 2300 | 8 | 5 | 5 | 800 / 1800 | 8 | 6 | 6 |
| 4000 and above | 1200 / 2700 | 8 | 5 | 5 | 800 / 1800 | 8 | 5 | 5 | 400 / 900 | 5 | 3 | 3 |
If the actual TOW is lower than the MTOW calculated using above method:
The speeds determined
without failure and associated with the actual TOW may
be retained provided that they are all lower than the speeds calculated
using above method.
Check that the corrected V1 is equal to or above the minimum V1 value shown
on the RTOW chart (due to VMCG limitation).
If the corrected V1 is lower than the minimum V1:
Take this last value
as V1.
Further decrease the weight by 3000 kg ( 6600 lb) per kt difference between both values.
Check that the corrected VR is equal to or above the minimum VR value shown
on the RTOW chart (due to VMCA limitation).
If the corrected VR is lower than the minimum VR:
Takeoff cannot be performed using this method.
Check that the corrected V2 is equal to or above the minimum V2 value shown
on the RTOW chart (due to VMCA limitation).
If the corrected V2 is lower than the minimum V2:
Takeoff cannot be performed using this method.
Check that the corrected V2 is equal to or above the minimum V2 due to VMU limitation ( Refer to FCOM).
If the corrected V2 is lower than the minimum V2:
Takeoff cannot be performed using this method.
Landing performance computation:
Multiply the landing distances by 1.45.
- Takeoff
If the above method was used for takeoff performance computation:
Perform the takeoff
using full thrust (TOGA).
| 27-92-02A | Ground Spoiler Control System (ground spoiler control system inoperative) |
|---|
Applicable to: -
- General information
The autobrake function is not
available. Refer to OpsProc AUTO/BRK Function.
| CAUTION: | One or both thrust
reversers may not deploy at landing. Consequently, for performance
determination, do not take into account the credit of the thrust reversers. |
- Flight preparation/limitations
Takeoff
performance computation
The takeoff performance must
be determined by using OCTOPUS program or other equivalent program
with present failure case taken into account.
Launch PEP.
Landing performance computation
Multiply the landing distances by 1.20.
| 27-92-02A | Ground Spoiler Control System (Ground spoiler control system inoperative) |
|---|
Applicable to: -
- General information
The autobrake function is
not available. Refer to OpsProc AUTO/BRK Function
| CAUTION: | One or both thrust
reversers may not deploy at landing. Consequently, for performance
determination, do not take into account the credit of the thrust reversers. |
- Flight preparation/limitations
The following penalties
may be used for takeoff and landing performance determination if no
takeoff and landing data (predetermined by using OCTOPUS program or
other equivalent program with present failure case) is available.
Takeoff performance computation:
The method explained hereafter
allows the determination of the MTOW and associated speeds
(V1, VR, V2), by applying decrements
on the MTOW and associated speeds computed in normal conditions
(i.e. all systems operative).
| WARNING: |
|
How to proceed ?
- Read, in 0 kt wind column of the takeoff chart computed in normal condition, the MTOW and associated speeds (V1, VR, V2) corresponding to the actual temperature, even in the case of headwind (the method does not take into account the headwind benefit on takeoff performance).
- Apply the QNH and/or bleed corrections, if any, to determine the MTOW.
- Enter the following table to determine the MTOW and speed decrements.
- Applying these decrements, calculate the MTOW and associated speeds corresponding to the actual temperature.
| CAUTION: | For runway lengths below 1,500
m, do not use the following table. |
DECREMENTS (ΔW, ΔV1, ΔVR, ΔV2) WHEN GROUND SPOILER CONTROL
SYSTEM IS INOPERATIVE | ||||||||||||
|---|---|---|---|---|---|---|---|---|---|---|---|---|
| RUNWAY LENGTH (m) | CONFIGURATION | |||||||||||
| 1+F | 2 | 3 | ||||||||||
| ΔW (kg/lb) | ΔV1 (kt) | ΔVR (kt) | ΔV2 (kt) | ΔW (kg/lb) | ΔV1 (kt) | ΔVR (kt) | ΔV2 (kt) | ΔW (kg/lb) | ΔV1 (kt) | ΔVR (kt) | ΔV2 (kt) | |
| 1500 | 2200 / 4800 | 6 | 1 | 1 | 2400 / 5200 | 8 | 7 | 7 | 2400 / 5200 | 8 | 6 | 6 |
| 2000 | 1600 / 3500 | 6 | 3 | 3 | 1400 / 3000 | 7 | 4 | 4 | 1800 / 3900 | 8 | 4 | 4 |
| 2500 | 1600 / 3500 | 6 | 3 | 3 | 1400 / 3000 | 7 | 4 | 4 | 1800 / 3900 | 9 | 5 | 5 |
| 3000 | 1200 / 2600 | 7 | 4 | 4 | 1200 / 2600 | 8 | 5 | 5 | 1400 / 3000 | 9 | 6 | 6 |
| 3500 | 1200 / 2600 | 8 | 5 | 5 | 800 / 1700 | 8 | 5 | 5 | 800 / 1700 | 8 | 6 | 6 |
| 4000 and above | 1200 / 2600 | 9 | 5 | 5 | 1000 / 2200 | 9 | 7 | 7 | 200 / 400 | 1 | 2 | 2 |
If the actual TOW is lower than the MTOW calculated using above method:
The speeds determined
without failure and associated with the actual TOW may
be retained provided that they are all lower than the speeds calculated
using above method.
Check that the corrected V1 is equal to or above the minimum V1 value shown
on the RTOW chart (due to VMCG limitation).
If the corrected V1 is lower than the minimum V1:
Take this last value
as V1.
Further decrease the weight by 3000 kg ( 6600 lb) per kt difference between both values.
Check that the corrected VR is equal to or above the minimum VR value shown
on the RTOW chart (due to VMCA limitation).
If the corrected VR is lower than the minimum VR:
Takeoff cannot be performed using this method.
Check that the corrected V2 is equal to or above the minimum V2 value shown
on the RTOW chart (due to VMCA limitation).
If the corrected V2 is lower than the minimum V2:
Takeoff cannot be performed using this method.
Check that the corrected V2 is equal to or above the minimum V2 due to VMU limitation ( Refer to FCOM).
If the corrected V2 is lower than the minimum V2:
Takeoff cannot be performed using this method.
Landing performance computation:
Multiply the landing distances by 1.45.
- Takeoff
If the above method was used for takeoff performance computation:
Perform the takeoff
using full thrust (TOGA).
| 27-92-02A | Ground Spoiler Control System (Ground spoiler control system inoperative) |
|---|
Applicable to: -
- General information
The autobrake function is
not available. Refer to OpsProc AUTO/BRK Function
| CAUTION: | One or both thrust
reversers may not deploy at landing. Consequently, for performance
determination, do not take into account the credit of the thrust reversers. |
- Flight preparation/limitations
The following penalties
may be used for takeoff and landing performance determination if no
takeoff and landing data (predetermined by using OCTOPUS program or
other equivalent program with present failure case) is available.
Takeoff performance computation:
The method explained hereafter
allows the determination of the MTOW and associated speeds
(V1, VR, V2), by applying decrements
on the MTOW and associated speeds computed in normal conditions
(i.e. all systems operative).
| WARNING: |
|
How to proceed ?
- Read, in 0 kt wind column of the takeoff chart computed in normal condition, the MTOW and associated speeds (V1, VR, V2) corresponding to the actual temperature, even in the case of headwind (the method does not take into account the headwind benefit on takeoff performance).
- Apply the QNH and/or bleed corrections, if any, to determine the MTOW.
- Enter the following table to determine the MTOW and speed decrements.
- Applying these decrements, calculate the MTOW and associated speeds corresponding to the actual temperature.
| CAUTION: | For runway lengths below 1,500
m, do not use the following table. |
DECREMENTS (ΔW, ΔV1, ΔVR, ΔV2) WHEN GROUND SPOILER CONTROL
SYSTEM IS INOPERATIVE | ||||||||||||
|---|---|---|---|---|---|---|---|---|---|---|---|---|
| RUNWAY LENGTH (m) | CONFIGURATION | |||||||||||
| 1+F | 2 | 3 | ||||||||||
| ΔW (kg/lb) | ΔV1 (kt) | ΔVR (kt) | ΔV2 (kt) | ΔW (kg/lb) | ΔV1 (kt) | ΔVR (kt) | ΔV2 (kt) | ΔW (kg/lb) | ΔV1 (kt) | ΔVR (kt) | ΔV2 (kt) | |
| 1500 | 2400 / 5200 | 6 | 2 | 2 | 2600 / 5700 | 7 | 2 | 2 | 2100 / 4600 | 6 | 2 | 2 |
| 2000 | 2400 / 5200 | 6 | 2 | 2 | 2200 / 4800 | 4 | 1 | 1 | 2200 / 4800 | 6 | 2 | 2 |
| 2500 | 1500 / 3300 | 3 | 1 | 1 | 1700 / 3700 | 3 | 1 | 1 | 2000 / 4400 | 5 | 2 | 2 |
| 3000 | 2500 / 5500 | 10 | 9 | 9 | 2200 / 4800 | 7 | 7 | 7 | 1600 / 3500 | 8 | 5 | 5 |
| 3500 | 1700 / 3700 | 7 | 6 | 6 | 1800 / 3900 | 7 | 6 | 6 | 1500 / 3300 | 9 | 5 | 5 |
| 4000 and above | 1400 / 3000 | 7 | 4 | 4 | 1500 / 3300 | 8 | 5 | 5 | 1300 / 2800 | 9 | 5 | 5 |
If the actual TOW is lower than the MTOW calculated using above method:
The speeds determined
without failure and associated with the actual TOW may
be retained provided that they are all lower than the speeds calculated
using above method.
Check that the corrected V1 is equal to or above the minimum V1 value shown
on the RTOW chart (due to VMCG limitation).
If the corrected V1 is lower than the minimum V1:
Take this last value
as V1.
Further decrease the weight by 3000 kg ( 6600 lb) per kt difference between both values.
Check that the corrected VR is equal to or above the minimum VR value shown
on the RTOW chart (due to VMCA limitation).
If the corrected VR is lower than the minimum VR:
Takeoff cannot be performed using this method.
Check that the corrected V2 is equal to or above the minimum V2 value shown
on the RTOW chart (due to VMCA limitation).
If the corrected V2 is lower than the minimum V2:
Takeoff cannot be performed using this method.
Check that the corrected V2 is equal to or above the minimum V2 due to VMU limitation ( Refer to FCOM).
If the corrected V2 is lower than the minimum V2:
Takeoff cannot be performed using this method.
Landing performance computation:
Multiply the landing distances by 1.35.
- Takeoff
If the above method was used for takeoff performance computation:
Perform the takeoff
using full thrust (TOGA).
| 27-92-02A | Ground Spoiler Control System (ground spoiler control system inoperative) |
|---|
Applicable to: -
- General information
The autobrake
function is not available. Refer to OpsProc AUTO/BRK Function
| CAUTION: | One or both thrust
reversers may not deploy at landing. Consequently, for performance
determination, do not take into account the credit of the thrust reversers. |
- Flight preparation/limitations
Takeoff performance computation
The takeoff performance must be determined
by using OCTOPUS program or other equivalent program with present
failure case taken into account.
Launch PEP.
Landing
performance computation
Multiply the landing distances by 1.35.
| 27-92-02A | Ground Spoiler Control System (ground spoiler control system inoperative) |
|---|
Applicable to: -
- General information
The autobrake
function is not available. Refer to OpsProc AUTO/BRK Function
| CAUTION: | One or both thrust
reversers may not deploy at landing. Consequently, for performance
determination, do not take into account the credit of the thrust reversers. |
- Flight preparation/limitations
Takeoff performance computation
The takeoff performance must be determined
by using OCTOPUS program or other equivalent program with present
failure case taken into account.
Launch PEP.
Landing
performance computation
Multiply the landing distances by 1.15.
| 27-92-02A | Ground Spoiler Control System (ground spoiler control system inoperative) |
|---|
Applicable to: -
- General information
The autobrake
function is not available. Refer to OpsProc AUTO/BRK Function
| CAUTION: | One or both thrust
reversers may not deploy at landing. Consequently, for performance
determination, do not take into account the credit of the thrust reversers. |
- Flight preparation/limitations
Takeoff performance computation
The takeoff performance must be determined
by using OCTOPUS program or other equivalent program with present
failure case taken into account.
Launch PEP.
Landing
performance computation
Multiply the landing distances by 1.50.